(n63010a-il) NACA 63A010 AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63-010A airfoilMax thickness 10% at 35% chordMax camber 0% at 0% chordSource UIUC Airfoil Coordinates Database

(n63012a-il) NACA 63012A AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63-012A airfoilMax thickness 12% at 35% chordMax camber 0% at 0% chordSource UIUC Airfoil Coordinates Database

(n63015a-il) NACA 63-015A AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63-015A airfoilMax thickness 15% at 35% chordMax camber 0% at 0% chordSource UIUC Airfoil Coordinates Database

(n63210-il) NACA 63-210 AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63-210 airfoilMax thickness 10% at 35% chordMax camber 1.1% at 60% chordSource UIUC Airfoil Coordinates Database

(n63212-il) NACA 63-212 AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63(1)-212 airfoilMax thickness 12% at 34.9% chordMax camber 1.1% at 55% chordSource UIUC Airfoil Coordinates Database

(n63215-il) NACA 63-215 AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63(2)-215 airfoilMax thickness 15% at 34.9% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(n63215b-il) NACA 63(2)-215 MOD BAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA-NASA/AMES/Hicks 63(2)-215 MOD B airfoilMax thickness 15% at 30% chordMax camber 1.5% at 10% chordSource UIUC Airfoil Coordinates Database

(n63412-il) NACA 63-412 AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63(1)-412 airfoilMax thickness 12% at 34.9% chordMax camber 2.2% at 50% chordSource UIUC Airfoil Coordinates Database

(n63415-il) NACA 63-415 AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63(2)-415 airfoilMax thickness 15% at 34.9% chordMax camber 2.2% at 50% chordSource UIUC Airfoil Coordinates Database

(n64008a-il) NACA 64-008A AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64-008A airfoilMax thickness 8% at 40% chordMax camber 0% at 0% chordSource UIUC Airfoil Coordinates Database

(n64012-il) NASA/LANGLEY 64-012 AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64(1)-012 airfoilMax thickness 12% at 40% chordMax camber 0% at 0% chordSource UIUC Airfoil Coordinates Database

(n64012a-il) NACA 64-012A AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64(1)-012A airfoilMax thickness 12% at 40% chordMax camber 0% at 0% chordSource UIUC Airfoil Coordinates Database

(n64015-il) NACA 642-015 AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64(2)-015 airfoilMax thickness 15% at 35% chordMax camber 0% at 0% chordSource UIUC Airfoil Coordinates Database

(n64015a-il) NACA 642-015A AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64(2)-015A airfoilMax thickness 15% at 40% chordMax camber 0% at 0% chordSource UIUC Airfoil Coordinates Database

(n64108-il) NACA 64-108 AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64-108 airfoilMax thickness 8% at 40% chordMax camber 0.6% at 50% chordSource UIUC Airfoil Coordinates Database

(n64110-il) NACA 64-110 AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64-110 airfoilMax thickness 10% at 40% chordMax camber 0.6% at 50% chordSource UIUC Airfoil Coordinates Database

(n64212-il) NACA 64(1)-212Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64(1)-212 airfoilMax thickness 12% at 40% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(n64212ma-il) NACA 64(1)-212 MOD AAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA-NASA/AMES/Hicks 63(1)-212 MOD A airfoilMax thickness 12% at 41.2% chordMax camber 2.5% at 21.5% chordSource UIUC Airfoil Coordinates Database

(n64212mb-il) NACA 64(1)-212 MOD BAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA-NASA/AMES/Hicks 63(1)-212 MOD B airfoilMax thickness 12% at 34.9% chordMax camber 1.5% at 9.9% chordSource UIUC Airfoil Coordinates Database

(n64215-il) NACA 64-215 AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64(2)-215 airfoilMax thickness 15% at 34.9% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(n66021-il) NACA 66-021 AIRFOILAirfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 66(4)-021 airfoilMax thickness 21% at 45% chordMax camber 0% at 0% chordSource UIUC Airfoil Coordinates Database

(naca63206-il) NACA 63-206Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63-206 airfoilMax thickness 6% at 35% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca63209-il) NACA 63-209Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63-209 airfoilMax thickness 9% at 35% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca632615-il) NACA 63(2)-615Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63(2)-615 airfoilMax thickness 15% at 34.8% chordMax camber 3.3% at 50% chordSource UIUC Airfoil Coordinates Database

(naca632a015-il) NACA 63(2)A-015Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63(2)A-015 airfoilMax thickness 15% at 37.1% chordMax camber 1.7% at 14.6% chordSource UIUC Airfoil Coordinates Database

(naca633018-il) NACA 63(3)-018Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63(3)-018 airfoilMax thickness 18% at 33.9% chordMax camber 0% at 0% chordSource UIUC Airfoil Coordinates Database

(naca633218-il) NACA 63(3)-218Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63(3)-218 airfoilMax thickness 18% at 34.9% chordMax camber 1.1% at 24.9% chordSource UIUC Airfoil Coordinates Database

(naca633418-il) NACA 63Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63Max thickness 18% at 33.9% chordMax camber 2.2% at 50% chordSource UIUC Airfoil Coordinates Database

(naca633618-il) NACA 63(3)-618Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63(3)-618 airfoilMax thickness 18% at 34.7% chordMax camber 3.3% at 50% chordSource UIUC Airfoil Coordinates Database

(naca634221-il) NACA 63(4)-221Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63(4)-221 airfoilMax thickness 21% at 34.9% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca634421-il) NACA 63(4)-421Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63(4)-421 airfoilMax thickness 21% at 34.8% chordMax camber 2.2% at 50% chordSource UIUC Airfoil Coordinates Database

(naca63a210-il) NACA 63A210Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 63A210 airfoilMax thickness 10% at 34.9% chordMax camber 1.3% at 50% chordSource UIUC Airfoil Coordinates Database

(naca641112-il) NACA 64(1)-112Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64(1)-112 airfoilMax thickness 12% at 40% chordMax camber 0.6% at 50% chordSource UIUC Airfoil Coordinates Database

(naca64206-il) NACA 64-206Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64-206 airfoilMax thickness 6% at 40% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca64208-il) NACA 64-208Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64-208 airfoilMax thickness 8% at 40% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca64209-il) NACA 64-209Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64-209 airfoilMax thickness 9% at 40% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca64210-il) NACA 64-210Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64-210 airfoilMax thickness 10% at 40% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca642215-il) NACA 64(2)-215Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64(2)-215 airfoilMax thickness 15% at 34.9% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca642415-il) NACA 64(2)-415Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64(2)-415 airfoilMax thickness 15% at 34.9% chordMax camber 2.2% at 50% chordSource UIUC Airfoil Coordinates Database

(naca643218-il) NACA 64(3)-218Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64(3)-218 airfoilMax thickness 18% at 34.9% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca643418-il) NACA 64(3)-418Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64(3)-418 airfoilMax thickness 17.9% at 34.8% chordMax camber 2.2% at 50% chordSource UIUC Airfoil Coordinates Database

(naca643618-il) NACA 64(3)-618Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64(3)-618 airfoilMax thickness 17.9% at 34.7% chordMax camber 3.3% at 50% chordSource UIUC Airfoil Coordinates Database

(naca644221-il) NACA 64(4)-221Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64(4)-221 airfoilMax thickness 21% at 34.9% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca644421-il) NACA 64(4)-421Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64(4)-421 airfoilMax thickness 20.9% at 34.8% chordMax camber 2.2% at 50% chordSource UIUC Airfoil Coordinates Database

(naca64a010-il) NACA 64A-010 10.0%Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64A010 airfoilMax thickness 10% at 40% chordMax camber 0% at 0% chordSource UIUC Airfoil Coordinates Database

(naca64a210-il) NACA 64A210Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64A210 airfoilMax thickness 10% at 40% chordMax camber 1.3% at 50% chordSource UIUC Airfoil Coordinates Database

(naca64a410-il) NACA 64A410Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 64A410 airfoilMax thickness 10% at 39.9% chordMax camber 2.7% at 50% chordSource UIUC Airfoil Coordinates Database

(naca651212-il) NACA 65(1)-212Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 65(1)-212 airfoilMax thickness 12% at 40% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca651212a06-il) NACA 65(1)-212 a=0.6Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 65(1)-212 a=0.6 airfoilMax thickness 12% at 40% chordMax camber 1.5% at 50% chordSource UIUC Airfoil Coordinates Database

(naca651412-il) NACA 65(1)-412Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 65(1)-412 airfoilMax thickness 12% at 39.9% chordMax camber 2.2% at 50% chordSource UIUC Airfoil Coordinates Database

(naca65206-il) NACA 65-206Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 65-206 airfoilMax thickness 6% at 40% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca65209-il) NACA 65-209Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 65-209 airfoilMax thickness 9% at 40% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca65210-il) NACA 65-210Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 65-210 airfoilMax thickness 10% at 40% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca652215-il) NACA 65(2)-215Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 65(2)-215 airfoilMax thickness 15% at 40% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca652415-il) NACA 65(2)-415Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 65(2)-415 airfoilMax thickness 15% at 39.9% chordMax camber 2.2% at 50% chordSource UIUC Airfoil Coordinates Database

(naca652415a05-il) NACA 65(2)-415 a=0.5Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 65(2)-415 a=0.5 airfoilMax thickness 15% at 39.9% chordMax camber 3% at 45% chordSource UIUC Airfoil Coordinates Database

(naca653218-il) NACA 65(3)-218Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 65(3)-218 airfoilMax thickness 18% at 39.9% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca653618-il) NACA 65(3)-618Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 65(3)-618 airfoilMax thickness 18% at 39.8% chordMax camber 3.3% at 50% chordSource UIUC Airfoil Coordinates Database

(naca65410-il) NACA 65-410Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 65-410 airfoilMax thickness 10% at 39.9% chordMax camber 2.2% at 50% chordSource UIUC Airfoil Coordinates Database

(naca654221-il) NACA 65(4)-221Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 65(4)-221 airfoilMax thickness 21% at 39.9% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca654421-il) NACA 65(4)-421Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 65(4)-421 airfoilMax thickness 21% at 39.9% chordMax camber 2.2% at 50% chordSource UIUC Airfoil Coordinates Database

(naca654421a05-il) NACA 65(4)-421 a=0.5Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 65(4)-421 a=0.5 airfoilMax thickness 21% at 39.9% chordMax camber 3% at 45% chordSource UIUC Airfoil Coordinates Database

(naca66-018-il) NACA 66-018Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 66-018 airfoilMax thickness 18% at 45% chordMax camber 0% at 0% chordSource UIUC Airfoil Coordinates Database

(naca661212-il) NACA 66(1)-212Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 66(1)-212 airfoilMax thickness 12% at 45% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca66206-il) NACA 66-206Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 66-206 airfoilMax thickness 6% at 45% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca66209-il) NACA 66-209Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 66-209 airfoilMax thickness 9% at 45% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca66210-il) NACA 66-210Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 66-210 airfoilMax thickness 10% at 45% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca662215-il) NACA 66(2)-215Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 66(2)-215 airfoilMax thickness 15% at 45% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca662415-il) NACA 66(2)-415Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 66(2)-415 airfoilMax thickness 15% at 45% chordMax camber 2.2% at 50% chordSource UIUC Airfoil Coordinates Database

(naca663218-il) NACA 66(3)-218Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 66(3)-218 airfoilMax thickness 18% at 45% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca663418-il) NACA 66(3)-418Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 66(3)-418 airfoilMax thickness 18% at 44.9% chordMax camber 2.2% at 50% chordSource UIUC Airfoil Coordinates Database

(naca664221-il) NACA 66(4)-221Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 66(4)-221 airfoilMax thickness 21% at 45% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database

(naca671215-il) NACA 67Airfoil detailsSend to airfoil plotterAdd to comparisonLednicer format dat fileSelig format dat fileSource dat file

NACA 67Max thickness 15% at 50% chordMax camber 1.1% at 50% chordSource UIUC Airfoil Coordinates Database